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Research Papers: Gas Turbines: Structures and Dynamics

The Deduction of the Integral and the Estimation of the Local Core Rotation Ratio by Telemetric Pressure Measurements in a Two Cavity Test Rig

[+] Author and Article Information
Wieland Uffrecht

 Technische Universität Dresden, Institute of Fluid Mechanics, 01062 Dresden, Germanywieland.uffrecht@tu-dresden.de

André Günther

 Technische Universität Dresden, Institute of Fluid Mechanics, 01062 Dresden, Germanyandre.guenther@tu-dresden.de

J. Eng. Gas Turbines Power 134(4), 042502 (Jan 25, 2012) (12 pages) doi:10.1115/1.4004452 History: Received April 01, 2011; Accepted June 20, 2011; Published January 25, 2012; Online January 25, 2012

The heat transfer in rotating cavities, as found in the internal air system of gas turbines, is mainly governed by the flow passing through these specific machine structures. The core rotation ratio represents the circumferential velocity, and is thought to be an influential flow parameter for heat transfer in rotating cavities with radial flow-through. Therefore, this paper focuses on deducing the core rotation ratio and the estimation of its local distribution using telemetric pressure measurements. The local core rotation ratio depends on the radial pressure distribution in a rotating cavity system. Thus, an integral core rotation ratio can be determined from pressure measurements in the rotating cavity system. A flow structure-based approximation of the measurements allows an estimation of the radial distribution of the core rotation ratio in the rotating cavity. The results of the measurements with varied flow rates and revolving speeds are presented, as well as a discussion of the fit parameters and their dependency on the operation mode of the test rig.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 11

Core rotation ratio βb at the shroud versus integral ratio of the Reynolds numbers assuming loss coefficient ξ = 0.005, all measurements, inner shaft speed not visible, length/diameter = 1.1 for the inlet holes of the shroud

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Figure 10

Integral core rotation ratio βi versus another ratio of Reynolds numbers for all measurements, symbol size proportional to shroud Mach number for Tf1

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Figure 9

Integral core rotation ratio βi versus integral ratio of the Reynolds numbers as noted in Eq. 26 for all measurements, for different angular speeds of the rotor and the inner shaft, for different temperature and for both drainage directions. Rotor speed not visible; upper fit for βi via Eq. 3, lower fit for βi via Eq. 4 — points not depicted.

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Figure 8

Loss coefficient versus integral ratio of the Reynolds numbers from Eq. 26 of all measurements for different angular speeds of the rotor and the inner shaft, for different temperatures, and both drainage directions. Rotor speed not visible; fit from all measurements; measurement error horizontal smaller than the symbol size; measurement error vertical depicted for the cases I and III; error for case II smaller than symbol size.

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Figure 7

Loss coefficient versus integral ratio of the Reynolds numbers as noted in Eq. 26 for different angular rotor speeds, for different temperature, for both drainage directions and for the drainage to the right calculated with βb  = 0.95

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Figure 6

Telemetric measurements of the temperature corrected according to Eq. 8 with the radial temperature distribution based on a constant polytropic exponent and the circumferential velocity for the three cases of Table 2, pressure and core rotation ratio depicted in Fig. 5

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Figure 5

Telemetric measurements of the static pressure with the radial pressure distribution based on the fit function and the radial core rotation ratio for the three cases of Table 2, temperature and velocity depicted in Fig. 6

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Figure 4

Integral core rotation ratio βi versus ratio of rotational and radial Reynolds number for different temperatures, for varied rotor revolving speed and for different drainage directions, upper fit represents the calculation of βi with Eq. 3, while the lower fit is for a polytropic calculation of βi with Eq. 4 — data points not depicted

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Figure 3

Experimental program for radial flow and drainage towards the center disk with radial mass flow rate versus revolving speed of the rotor, where cold is approximately 40 °C and warm is about 100 °C, with different co- and contra rotating revolving speeds for the inner shaft

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Figure 2

Cavity 1 with radial flowthrough with the instrumentation described in Table 1

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Figure 1

Two cavity rotor test rig for flow and heat transfer examination

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